Aeroplane



March 10, 1925. 1,528,970

R. A. GRIFFITH AEROPLANE Filed March 2 1924 m P 7 INVENTOR PatentedMerc- .l@,

UNITED STATES RUPERT AUGUSTUS GRIFFITH, OF MORSEMERE, NEW JERSEY.

AEROPLANE.

Application filed March 26, 1924. Serial No. 702,045.

To all whom, it may concern:

Be it known that RUPERT A. GRIFFITH, a citizen of the United States,residing at Morsernere, in the county of Bergen and State of New Jersey,has invented certain new and useful Improvements in Aeroplanes, of whichthe following is a specification.

My invention relates to improvements in aeroplanes and has for itsobject to provide an aeroplane of the monoplane type de-. signed toascend quickly, have the least w1nd resistance and great speed.

A further object of the invention is to provide shock absorbing meansassociated with the running gear adapted to absorb the shock to theplane incidental to landing.

Another object of the invention is to provide an aeroplane of theabove-menzo'tioned character which is simple and'durable inconstruction, reliable and eflicient in operation and inexpensive tomanufacture.

.Other objects and advantages of the invention will be apparent duringthe course of the following description.

In the accompanying drawing, forming a part of this specification and inwhich like numerals are employed to designate like to parts throughoutthe same,

Figure 1, is a side elevation of the plane,

Figure 2, is a top view of the same, Figure 3, is a longitudinalsectional view of the wing, and, as 'Figure 4-, is a detail view of theshock absorber for the running gear.

Referring to the drawing, wherein for the purpose ofgillustration I haveshown a preferred embodiment of my invention, the numeral 5 designatesthe fuselage of the plane having its nose 6 streamline shape and itstail '2 tapered. 'llhe under surface of the fuselage behind the nose iscambered forming a pocket 8, to facilitate the of 45 the fuselage. Apropeller 9 is mounted in front of the fuselage and a pair of coelr pits10 are positioned behind the propeller. The usual rudder 11 is hingeollyconnected to the vertical stabilizer 12 and the elevators 5t? 13 to thehorizontal stabilizers 14-. The stabilizers have their outer edgesinclined forwardly towards the fuselage and are streamline shape todeflect the air currents so as not to interfere with the control of theill 1 the spring having its other end connected 3 versely ext The wings15 extend laterally from the sides of the fuselage having their trailingedges 16 converging inwardly towards the tail, so the wing spread istriangular in shape. The upper surface of the wings, at their leadingedge, is of convex shape, as at 17, and the under surface is curveddownwardly, as at 18, presenting a streamline shaped nose. To the rearof the nose the under surface of the wings are cambered, at 19. formingpockets to facilitate the lift of the plane. The covering of the wingsis braced by suitable ribs 20, and guy wires 21 extending from thetripod 22 carried by the fuselage, brace the marginal edges of thewings.

On the ground the plane is supported at its forward end by the runninggear 23 and at its rear end by the tail skid 24. As more clearly shownin Fig. 4:, the running gear is equipped with shock absorbing meansconsisting of a lever 25 pivotally connected to the bearing, plate 26,by the pivot pin 27, and having its end 28 pivoted to the block 29slidably mounted in the vertical slot 30 and supporting the axle 34 onwhich the wheels 35 are mounted. The .opposite end 31 of the lever isconnected to one end of the coil spring 32,

to the support 33 of the running gear.

It is to be understood that the form of my invention herewith shown anddescribed is to be taken as a preferred example of the same and thatcertain changes in the shape, size and arrangement of parts may beresorted to without departing from the spirit of the invention or thescope of the sub- In an aeroplane, the con a fuselage having astreamline and a cambered por adjacent said now extending lat fuselageon a present a convened fuselage, and a pair of wings extendingtransversely extending concaved groove at horizontally from the sides ofsaid fusea point in vertical alinement with the rear lage having theirtrailing edges converging portion of the convexed surface. 10 towardsthe rear of the fuselage, said WlIlgS In testimony whereof I afiix mysigna- 5 having the upper surface of their leading ture.

edges raised to present a convexed surface, the under surface of saidWings having a RUPERT AUGUSTUS GRIFFITH.

